Abstract: A turbine engine cooling arrangement includes a core passage for receiving a core flow for combustion, a first airflow source including a first passage adjacent the core passage for conveying a first airflow, and a second airflow source including a second passage adjacent the first passage for conveying a second airflow. A heat exchanger is thermally connected with the first passage and the second passage for transferring heat between the first airflow and the second airflow.

Abstract: A gas turbine engine includes a fan nacelle and a core nacelle spaced radially inwardly of the fan nacelle to define a bypass flowpath. The engine includes a scoop to direct air from the bypass flowpath into an engine core. The scoop is comprised of a first piece extending outwardly of an outer surface the core nacelle to define an air inlet and a second piece extending inwardly of the core nacelle to define an air outlet.

Abstract: A nacelle for a turbofan propulsion system that extends along a centerline includes a forward cowling and an aft cowling. To improve the fit of a turbofan propulsion system in the space between the wing and ground of a fixed-wing aircraft, the aft cowling of the nacelle is modified. The aft cowling has a non-circular cross-sectional geometry disposed in a plane substantially perpendicular to the centerline. The non-circular cross-sectional geometry includes a radially recessed section disposed between first and second curved sections. The first and the second curved sections each have a radius that is greater than a radial distance between the centerline and a center point of the radially recessed section.

Abstract: A method of thermal management for a gas turbine engine comprising selectively positioning a valve to communicate a bypass flow into either an Environmental Control System (ECS) pre-cooler or an Air Oil Cooler (AOC) “peaker” through a common inlet.

Abstract: A gas turbine engine includes a fan nacelle and a core nacelle spaced radially inwardly of the fan nacelle to define a bypass flowpath. The engine includes a scoop to direct air from the bypass flowpath into an engine core. The scoop is comprised of a first piece extending outwardly of an outer surface the core nacelle to define an air inlet and a second piece extending inwardly of the core nacelle to define an air outlet.

Abstract: A nozzle assembly for a gas turbine engine includes a door axially slidable relative to a passage in communication with a secondary flow path to regulate the secondary flow though the passage.

Abstract: A nozzle section of a gas turbine engine includes a regulator system in fluid communication with a secondary flow duct and a tertiary flow duct to selectively regulate communication of secondary airflow into the tertiary flow duct.

Abstract: A gas turbine engine includes an exhaust liner having cold and hot sheets radially spaced from one another and interconnected by a band arranged in a cavity between the hot and cold sheets. In one example, the band is Z-shaped to permit thermal growth of the hot sheets relative to the cold sheets in the axial and radial directions. The hot sheets include axially adjacent portions that provide slots that are in fluid communication with the space. Cooling fluid is provided to the cavity through impingement jets in the cold sheet. The slots are arranged radially between the hot sheet portions.

Abstract: A thrust reverser blocker door assembly for use in turbofan engines includes an engine nacelle with an aft translating cowl that is movable from a stowed position to a deployed position. An engine case is disposed within the engine nacelle forming an airflow duct therebetween. A gap is uncovered when the translating cowl is moved into the deployed position, and a cascade vane set is positioned in the gap. A blocker door covers the cascade vane set while in the stowed position and blocks a portion of the airflow duct while in the deployed position. A geometrically shaped drag link is pivotally connected to the engine case at a first end and connected to the blocker door at a second end. While in the deployed position, the shape of the drag link provides clearance from the engine case.

Abstract: A nacelle for a turbofan propulsion system that extends along a centerline includes a forward cowling and an aft cowling. To improve the fit of a turbofan propulsion system in the space between the wing and ground of a fixed-wing aircraft, the aft cowling of the nacelle is modified. The aft cowling has a non-circular cross-sectional geometry disposed in a plane substantially perpendicular to the centerline. The non-circular cross-sectional geometry includes a radially recessed section disposed between first and second curved sections. The first and the second curved sections each have a radius that is greater than a radial distance between the centerline and a center point of the radially recessed section.

Abstract: Gas turbine engine systems and related methods involving heat exchange are provided. In this regard, a representative heat exchange system for a gas turbine engine includes: a heat exchanger; and a flow restrictor operative to selectively restrict a flow of gas flowing along an annular gas flow path; in an open position, the flow restrictor enabling gas to flow along the gas flow path and, in a closed position, the flow restrictor restricting the flow of gas such that at least a portion of the gas is provided to the heat exchanger, the heat exchanger being located radially outboard of the flow restrictor.

Abstract: A turbine engine exhaust nozzle is disclosed that includes an exhaust liner having a first attachment structure. A liner support member includes a second attachment structure. A pin cooperates with the first and second attachment structures and is configured to secure the exhaust liner relative to the liner support member. The pin includes first and second dimensions that are different than one another. The pin is inserted into apertures provided by the attachment structures, in one example. The pin is oriented to position the first and second dimensions in a manner providing increased clearance within the apertures. The pin is rotated to load the components and firmly secure the liner to the liner support member.

Abstract: A thrust reverser blocker door assembly for use in turbofan engines includes an engine nacelle with an aft translating cowl that is movable from a stowed position to a deployed position. An engine case is disposed within the engine nacelle forming an airflow duct therebetween. A gap is uncovered when the translating cowl is moved into the deployed position, and a cascade vane set is positioned in the gap. A blocker door covers the cascade vane set while in the stowed position and blocks a portion of the airflow duct while in the deployed position. A geometrically shaped drag link is pivotally connected to the engine case at a first end and connected to the blocker door at a second end. While in the deployed position, the shape of the drag link provides clearance from the engine case.

Abstract: A nozzle section of a gas turbine engine includes a regulator system in fluid communication with a secondary flow duct and a tertiary flow duct to selectively regulate communication of secondary airflow into the tertiary flow duct.

Abstract: Gas turbine engine systems involving variable nozzles with sliding doors are provided.

Abstract: A gas turbine engine includes an exhaust liner having cold and hot sheets radially spaced from one another and interconnected by a band arranged in a cavity between the hot and cold sheets. In one example, the band is Z-shaped to permit thermal growth of the hot sheets relative to the cold sheets in the axial and radial directions. The hot sheets include axially adjacent portions that provide slots that are in fluid communication with the space. Cooling fluid is provided to the cavity through impingement jets in the cold sheet. The slots are arranged radially between the hot sheet portions.

Abstract: A turbine engine cooling arrangement includes a core passage for receiving a core flow for combustion, a first airflow source including a first passage adjacent the core passage for conveying a first airflow, and a second airflow source including a second passage adjacent the first passage for conveying a second airflow. A heat exchanger is thermally connected with the first passage and the second passage for transferring heat between the first airflow and the second airflow.

Abstract: A turbine engine exhaust nozzle is disclosed that includes an exhaust liner having a first attachment structure. A liner support member includes a second attachment structure. A pin cooperates with the first and second attachment structures and is configured to secure the exhaust liner relative to the liner support member. The pin includes first and second dimensions that are different than one another. The pin is inserted into apertures provided by the attachment structures, in one example. The pin is oriented to position the first and second dimensions in a manner providing increased clearance within the apertures. The pin is rotated to load the components and firmly secure the liner to the liner support member.

Abstract: Gas turbine engine systems and related methods involving heat exchange are provided. In this regard, a representative heat exchange system for a gas turbine engine includes: a heat exchanger; and a flow restrictor operative to selectively restrict a flow of gas flowing along an annular gas flow path; in an open position, the flow restrictor enabling gas to flow along the gas flow path and, in a closed position, the flow restrictor restricting the flow of gas such that at least a portion of the gas is provided to the heat exchanger, the heat exchanger being located radially outboard of the flow restrictor.

Abstract: A corneal marker and a method of using a corneal marker are disclosed. The corneal marker includes a handle having a head coupled thereto. The inferior surface of the head includes a set of protuberances which form marking surfaces adapted to simultaneously engage corneal tissue. The marking surfaces form opposing sets of marks which allow a surgeon to form an incision of precise length and width. An alignment line on the superior and/or front surface of the marker facilitates the positioning thereof. A method of performing clear corneal surgery following the application of markings to the cornea is also provided.